Spacecraft commonly use multilayer insulation (MLI) on fixed panels and bodies to assist with thermal management of the system. This paper describes the design of an origami pattern that allows MLI to be used on deployable structures, specifically telescoping booms. Origami patterns have well-defined fold lines that provide predictable compression and extension of the MLI, which allows for high compression ratios from the deployed to the extended state with predictable thermal performance. Two four-layer MLI blankets were tested in thermal vacuum, one in its original unfolded state and the other folded using an octagonal origami pattern to characterize heat leak. The origami folds decreased thermal conductance and increased radiative heat transport through the MLI blanket with degradation factors empirically found to be $M_k=0.58\pm 0.1$ and $M_e=2.36\pm 0.16$, for the effective thermal conductance and emittance, respectively.

航天器通常在固定面板和主体上使用多层绝缘（MLI）来协助系统的热管理。本文介绍了折纸样式的设计，该折纸样式允许MLI用于可展开结构，特别是伸缩臂。折纸图案具有定义明确的折叠线，这些折叠线可提供MLI的可预测压缩和扩展，从而允许从展开状态到扩展状态的高压缩比以及可预测的热性能。在热真空下测试了两个四层MLI毯，其中一个处于原始展开状态，另一个使用八边形折纸图案折叠以表征热泄漏。折纸折叠会降低热导率，并增加通过MLI覆盖层的辐射热传输，并根据经验发现其降解因子为${\mathrm{中号}}_{ķ}=0.58\pm 0.1$ 和 ${\mathrm{中号}}_{Ë}=2.36\pm 0.16$分别表示有效的热导率和发射率。